In this work, the circumstances of eclipse for a circular satellites' orbit are studied. The time of passage of the ingress and egress points is calculated. Finally, the eclipse intervals of satellites' orbit are calculated. An application was done taken into account the effects of solar radiation pressure and Earth's oblateness on the orbital elements of circular orbit satellite.
In this paper, an algorithm is constructed for the determination of the perturbed motion, in both, the rectangular and the orbital elements of highly eccentric orbits in Earth's gravitational field with axial symmetry whatever the number N of the zonal harmonic coefficients may be. An application of the algorithm for the Explorer 28 satellite (e > 0.94) is given for two geopotential models corresponding to N = 2 and N = 36. In both examples extremely accurate predictions during the satellite life time are obtained.
The eclipse of a satellite in elliptical orbit is studied. The geocentric angle in the orbital plane between the perigee and conjunction point is determined. Eclipse times and duration of eclipse for elliptical orbits are obtained. The effects of the direct solar radiation pressure on the orbital elements are calculated taken into account the eclipses intervals. An application on the MOLNIYA 1-87 artificial satellite is done.
In this study, the locations of the equilibrium points of both triangular and collinear of restricted three-body problem and their stabilities are studied.This study was applied on ten binary asteroids. A code was constructed by MATHEMATICA language to obtain liberation points and their stabilities. On the other hand, the contour of zero velocity curves was displayed for two stable and unstable binaries.
The current work will be focused upon the study of the effects of the earth's gravitational field on the motion of an artificial satellite constellation and a computational model for this perturbation on the constellation orbit will be done; the earth's gravitational field up to second zonal harmonics is considered. This perturbation make a drift for the orbital elements of satellite constellation that make continues coverage and lead to a shift of the whole constellation structure. The equations of motion under effects of oblatenees force are solved numerically by using Rung-Kotta method. The results show that this model has efficiency to compute the perturbations for satellite constellation which already congruent with observing data.
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